[Federal Register Volume 77, Number 122 (Monday, June 25, 2012)]
[Proposed Rules]
[Pages 37829-37831]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-15461]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0671; Directorate Identifier 2011-NM-096-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede an existing airworthiness directive 
(AD) that applies to certain Airbus Model A330-243, -341, -342 and -343 
airplanes. The existing AD currently requires modifying certain cowl 
assemblies of the left- and right-hand thrust reversers. Since we 
issued that AD, the manufacturer has issued new life limits on certain 
thrust reverser C-duct assemblies. This proposed AD would require 
removing certain C-duct assemblies of the left- and right-hand thrust 
reversers from service at certain designated life limits, and would 
also add airplanes to the applicability. We are proposing this AD to 
prevent fatigue cracking of the hinges integrated into the 12 o'clock 
beam of the thrust reversers, which could result in separation of a 
thrust reverser from the airplane, and consequent reduced 
controllability of the airplane.

DATES: We must receive comments on this proposed AD by August 9, 2012.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 45 80; email [email protected]; Internet http://www.airbus.com. You may review copies of the referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, Washington. For information on the availability of 
this material at the FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Operations office (telephone (800) 647-5527) is 
in the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425) 
227-1138; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2012-0671; 
Directorate Identifier 2011-NM-096-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On December 2, 2005, we issued AD 2005-25-21, Amendment 39-14414 
(70 FR 73919, December 14, 2005). That AD required actions intended to 
address an unsafe condition on Airbus Model A330-243, -341, -342, and -
343 airplanes equipped with Rolls-Royce RB211 TRENT 700 engines.
    Since we issued AD 2005-25-21, Amendment 39-14414 (70 FR 73919, 
December 14, 2005), the European Aviation Safety Agency (EASA), which 
is the Technical Agent for the Member States of the European Community, 
has issued EASA Airworthiness Directive 2011-0018, dated February 3, 
2011 (referred to after this as ``the MCAI''), to correct an unsafe 
condition for the specified products. The MCAI has added Model A330-
243F airplanes to the applicability. The MCAI states:

    The life limits of the thrust reversers C-ducts are not 
addressed by the definition of the structural life limits of Safe 
Life items as defined in the A330 Airworthiness Limitations 
Section--ALS Part 1. As a result, these life limits are covered by 
an Airworthiness Directive (AD).
    These life limits are due to unexpected high fatigue loads 
(measured during certification tests) on the hinges integrated into 
the 12 o'clock beam, which forms the upper extreme edge of the 
thrust reverser C-Duct of Rolls Royce Trent 700 engines.
    The aim of the [Direction G[eacute]n[eacute]rale de l'Aviation 
Civile] (DGAC) France AD F-2001-528 was to mandate the life limits, 
depending of the modifications applied to the C-duct.
    Revision 1 of the DGAC France AD F-2001-528 deferred the 
accomplishment threshold of the modification to be applied in-
service from 6,000 flight cycles (FC) to 6,500 FC.
    Revision 2 of DGAC France AD F-2001-528 [which corresponds to 
FAA AD 2005-25-21, Amendment 39-14414 (70 FR 73919, December 14, 
2005)] was issued to update again the accomplishment threshold from 
6,500 FC to 7,200 FC.
    This [EASA] AD retains the requirements of DGAC France AD F-
2001-528 R2, which is superseded, and adds [certain] life limits.

The action required in this proposed AD is removing certain C-duct 
assemblies of the left- and right-hand thrust reversers from service at 
certain designated life limits. This proposed AD also adds Model A330-
243F airplanes to the applicability and revises the applicability to 
include all airplanes of the affected models. The unsafe condition is 
fatigue cracking of the hinges integrated into the 12 o'clock beam of 
the thrust reversers, which could result in separation of a thrust 
reverser from the airplane, and consequent reduced controllability of 
the airplane. You may obtain further information by examining the MCAI 
in the AD docket.

Relevant Service Information

    Airbus has issued Mandatory Service Bulletin A330-78-3010, Revision 
03, dated April 28, 2004. The actions

[[Page 37830]]

described in this service information are intended to correct the 
unsafe condition identified in the MCAI.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 17 products of U.S. registry. We estimate that it 
would take up to 48 work-hours per product to comply with the new basic 
requirements of this proposed AD. The average labor rate is $85 per 
work-hour. Based on these figures, we estimate the cost of the proposed 
AD on U.S. operators to be $69,360, or $4,080 per product.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by removing airworthiness directive 
(AD) 2005-25-21, Amendment 39-14414 (70 FR 73919, December 14, 2005), 
and adding the following new AD:

Airbus: Docket No. FAA-2012-0671; Directorate Identifier 2011-NM-
096-AD.

(a) Comments Due Date

    We must receive comments by August 9, 2012.

(b) Affected ADs

    This AD supersedes AD 2005-25-21, Amendment 39-14414 (70 FR 
73919, December 14, 2005).

(c) Applicability

    This AD applies to all Airbus Model A330-243, -243F, -341, -342 
and -343 airplanes, certificated in any category.

(d) Subject

    Air Transport Association (ATA) of America Code 78, Engine 
Exhaust.

(e) Reason

    This AD was prompted by new life limits on certain thrust 
reverser C-duct assemblies. We are issuing this AD to prevent 
fatigue cracking of the hinges integrated into the 12 o'clock beam 
of the thrust reversers, which could result in separation of a 
thrust reverser from the airplane, and consequent reduced 
controllability of the airplane.

(f) Compliance

    You are responsible for having the actions required by this AD 
performed within the compliance times specified, unless the actions 
have already been done.

(g) C-Duct Assembly Removal

    At the applicable compliance time specified in table 1 of this 
AD: Remove the applicable C-duct assemblies of the left- and right-
hand thrust reversers, in accordance with a method approved by 
either the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or the European Aviation Safety Agency 
(EASA) (or its delegated agent). Thereafter, for any C-duct assembly 
of the left- and right-hand thrust reversers installed after the 
effective date of this AD, before the accumulation of the applicable 
total flight cycles specified in table 1 of this AD: Remove the C-
duct assembly, in accordance with a method approved by either the 
Manager, International Branch, ANM 116, Transport Airplane 
Directorate, FAA; or the EASA (or its delegated agent).

                    Table 1--Part Removal Thresholds
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Part No.--                      Compliance times at the later of the
                                 times specified--
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HDTR3410L, HDTR3410R,           Before the              Within 3 months
 HDTR3411L, HDTR3411R,           accumulation of         after the
 HDTR3412R, HDTR3413R.           10,000 total flight     effective date
                                 cycles since the        of this AD.
                                 first installation of
                                 C-duct on the
                                 airplane.
HDTR3414L, HDTR3416R,           Before the              Within 3 months
 HDTR3417R that have been        accumulation of         after the
 modified in service as          10,000 total flight     effective date
 specified in Airbus Mandatory   cycles since the        of this AD.
 Service Bulletin                first installation of
 A330[dash]78[dash]3010, or      C-duct on the
 Rolls-Royce Service Bulletin    airplane.
 RB.211-78-C899, at 7,200
 total flight cycles or more
 since first installation on
 an airplane.

[[Page 37831]]

 
HDTR3414L, HDTR3416R,           Before the              Within 3 months
 HDTR3417R that have been        accumulation of         after the
 modified in production by       25,000 total flight     effective date
 Airbus Modification 47316; or   cycles since the        of this AD.
 modified in service as          first installation of
 specified in Airbus Mandatory   C-duct on the
 Service Bulletin                airplane.
 A330[dash]78[dash]3010, or
 Rolls-Royce Service Bulletin
 RB.211-78-C899, before the
 accumulation of 7,200 total
 flight cycles since first
 installation on an airplane.
HDTR3412L, HDTR3416L,           Before the              Within 3 months
 HDTR3417L, HDTR3414R,           accumulation of         after the
 HDTR3419R, HDTR3420R.           25,000 total flight     effective date
                                 cycles since the        of this AD.
                                 first installation of
                                 C-duct on the
                                 airplane.
HDTR3413L, HDTR3415R,           Before the              Within 3 months
 HDTR3415L, HDTR3418R.           accumulation of         after the
                                 40,000 total flight     effective date
                                 cycles since the C-     of this AD.
                                 duct was new.
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(h) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
Washington 98057-3356; telephone (425) 227-1138; fax (425) 227-1149. 
Information may be emailed to: [email protected]. 
Before using any approved AMOC, notify your appropriate principal 
inspector, or lacking a principal inspector, the manager of the 
local flight standards district office/certificate holding district 
office. The AMOC approval letter must specifically reference this 
AD.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.

(i) Related Information

    (1) Refer to MCAI EASA Airworthiness Directive 2011-0018, dated 
February 3, 2011; and Airbus Mandatory Service Bulletin A330-78-
3010, Revision 03, dated April 28, 2004; for related information.
    (2) For service information identified in this AD, contact 
Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 45 80; email [email protected]; 
Internet http://www.airbus.com. You may review copies of the 
referenced service information at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue SW., Renton, Washington. For 
information on the availability of this material at the FAA, call 
425-227-1221.

    Issued in Renton, Washington, on June 14, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-15461 Filed 6-22-12; 8:45 am]
BILLING CODE 4910-13-P